Beechcraft Twin-Bonanza B50 User manual

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Twin- onanza
MODB50
MAINTENANCE MANUAL
'Meech Oircraft Corporation (@ ill i chit a, I< ans as

50 - 590039-5
December 1953
REVISED 1 JUNE 1955
,,
MAINTENANCE
SERVICE DIVISION
BEECH AIRCRAFT CORPORATION
WICHITA 1, KANSAS

A
Page No.
Title
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LIST OF REVISIONS
PART I
PART II
PART III
PART
IV
D ate of Lat est
Revision
1 June 1955
1 June 1955
1
June 1955
1
Ju ne 1955
1
June 1955
1
June 1955
1
June 1955
1 June 1955
1
June 1955
1 June 1955
1 June 1955
1
June 1955
1 June 1955
1 June 1955
1 June 1955
1 June 1955
1 June 1955
1 June 1955
1 June 1955
ENTIRE SECTION REISSUED
PART V
PART VI
PART VIII
1 June 1955
1 June 1955
1
June 1955
1 June 1955
1
June 1955
1
June 1955
1
June 1955
1
June 1955
Revisions to this handbook are published for two basic reasons: First, to notify operators of Im-
proved techniques which may have been evolved since the original publicati on, and second, to de-
scribe production changes which have been made between model changes and which affect the util -
ity
or operating procedures of the airp lane,
Each revised p age carries a revision date and the revised matter on that page, except when it con-
stitutes more than half the page or Is a minor typog raphical correction or an lllustrati o n, Is indi-
cated by a black vertical rule In the margin be side the new text , In the list above appear all the re-
vised pages Issued against this book, with their current revision dates: The pages revised In suc-
ceeding revis ions likewise will be listed on this page, so that it becomes a running record of rev-
isions and a convenient method of checking the current status of the handbook. To keep the hand-
book up to date, Insert the revised pages in their prope r place, discarding the pages superseded by
the current revision.
Revised 1 June 1955

TABLE OF CONTENTS
Part
Page
I GENERAL
INFOilMATION. 1 - 1
1.1
Gener al Description 1 - 1
1.2
Gr ound Handling 1 - 1
1.3
Servicing In structions
1 - 1
II
AIRFRAME . 2 - 1
2.1
General 2 - 1
2.2
Fuselage. 2 - 1
2.3
Cen ter Wing Panel. 2 - 6
2.4 Engi.ne
Nacelle . 2 - 6
2,5
Outer Wing Pa nel . 2 - 6
2,6 Wing
Tip.
2 - 7
2.7 Control
Surfaces 2 - 7
2.8
Surface Control Systems 2 - 10
2.9
Landing G ear 2 - 18
III UTILITY S YS TE MS
3 - 1
3.1
Description . 3 - 1
3.2
Heating and V entila tin g System s 3 - 1
3.3
Engine Pr eheat Sys tem 3 - 4
3.4
Nose Steering Mechanism
3 - 5
IV POWER
PLANT 4 - 2
4.1
Description
4 - 2
4.2
Engine
4 - 2
4.3
Engine Co wling.
4 - 2
4.4
Pr ope ller and Co ntrol System • 4 - 3
4.9
Oil System
4 -27
4.10 Fuel S ys tem. 4 -34
4.11
Carburetor Air Intake System . 4 -35
4.12
Exhaust System
4 -35
4.13
Engine Coo ling System
4 -35
4.14
Igniti on System
4 -35
4.15
Vacuum System
4 -37
V INSTRUMENTS. 5 - 2
5.1
Instrument Panel
5 - 2
5,2
Flight Instruments
5 - 2
5.3
Engine Instruments
5 - 2
5,4
Instrument Removal
5 - 2
5,5
Instrument Installation
5 - 2
5.6
Instrument Vacuum System.
5 - 4
VI
ELECTRICAL SYSTEM . 6 - 1
6.1
Battery System
6 - 1
6.2
Starter System
6 - 1
6,3
Generator System . . 6 - 1
6.4
Interi or Lighting
6 - 4
6,5
Navigation Lights . 6 - 4
6.6
Landing Lights . 6 - 4
6.7
Stall Warning Circuit.
6 - 5
6,8
Dynamic Brake Relay
. . . . . 6 - 5

TABLE OF CONTENTS (Cont)
Part
VII ELECTRONIC SYSTEM •
7
.1 General Description
7 .2 Control Unit .
7
.3 Range Receiver .
7.4
Dynamotor . . .
7.5 VHF Receiver
7.6 VHF Transmitter
7.7 Range Antenna .
7.8 VHF Antenna . .
7.9 Mechanical Linkage . . .
7.10 Testing The B-50 Radio Set
VIII ELECT:PICAL WIRING DIAGRAMS.
8.1 Wiring Data . . . . . .
8.2 Wiring Diagrams . . . .
8- 1 Wing Flap Circuits . . • •
8- 2 Step Motor and Cigarette Lighter Circuits
8- 3 Landing Gear Circuits . . . .
8- 4 Cabin Heater Circuits . . . .
8- 5 Stall Warning Indicator Circuit
8- 6 Fuel Quantity Indicator Circuits
8- 7 Fuel Booster Pump Circuits
8- 8 Propeller Feathering Circuits .
8- 9 Oil Temperature Indicator Circuits
8-10 Ignition Circuits ....... .
8-11 Starter and Primer Circuits • . • •
8-12 Cylinder Head Temperature Indicator Circuits
8-13 Tachometer Circuits . , . . • ,
8-14 Turn and Bank Indicator Circuits
8-15 Pitot Heat Circuit . • . .
8-16 Power Distribution Circuit ...
8-17 Generator Circuits . . . . . .
8-18 Baggage, Red Instrument and Map Light Circuits
8-19 Cabin Dome, Cabin Step and Instrument Ultra-Violet Light Circuits
8-20 Navigation Light Circuits . . • . . . . . . . . . . . . . .
8-21 Landing Light Circuits . • . • . . . . . . • • . . . . . • . •
8-22 Basic Radio Circuit (ARC - R-llA, R-15, T-llB) Installation ...
Page
7 - 1
7 - 1
7 - 1
7 - 1
7 - 2
7 - 2
7 - 4
7 - 4
7 - 4
7 - 5
7 -
~
8 - 1
8 - 1
8 - 1
8 - 6
8 - 7
8 - 8
8 - 9
8 - 10
8 - 11
8 - 12
8 - 13
8 - 14
8 - 15
8 - 16
8 - 17
8 - 18
8 - 19
8 - 20
8 - 21
8 - 22
8 - 23
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24 v
8 - 25
8 - 26
8 - 27

INTRODUCTION
This handbook is inte nded as a guide in maintaining the BEECHCRAFT Model
B-50. Recommended maintenance proce du res have been grouped into seven
individual text sections and a sec ti on of sche mati c wirin g diagram s of the elec-
trical circuits used in the airplane. The text sections cover the basic airframe
and its related systems and componen t s, each sect ion containing both general
descriptive data and specific instructions. Each section has been numbered
within itself to facilitate incorporati ng peri o dic revisi on pages.
The illustrations in this manual which show the r o uting of cables, plumbing
and wiring harnesses are intended to give the reader a simplified, o verall
picture of the systems portrayed, in relati on to the rest of the airplane . To
achieve this purpose within the limits of a printed page, many details have been
omitted while the relative sizes of o ther items have been changed and, o ccasion-
ally, detail sections have been rotated in plane. These illustrations are pro-
vided only for reference in connectio n with the descriptive text, and not as the
basis for any maintenance opera ti ons. They are unsuitable, and were not intend-
ed, for use as rigging or reassembly guides. Never use them for such purposes.
Occasion ally, when a s pecific adjustment or assembly pr o cedure lends itself
to pictorial presentation a line drawing or photograph has been used, with spec-
ific information on its face rega rding points of measurement, adjusting points
or procedures, or similar data. Such information, specifically stated, may be
accepted as valid for direct u se in accomplishing the specific procedure in-
-:licated.
ll i
Revised 1 1une 1955

Three View Dimensional
iv

PART I
GENERAL INFORMATION
1.1
GENERAL DESCRIPTION
The Mod el B-50 BEEC H CRAFT is an all-metal,
twin-engine, low-wing monoplane powered by Lycom-
ing GO435-C2 horizontally-opposed engines develop-
ing 260 hp for take- off. The B-50 has a design gross
weight of 6000 pounds and uses BEEC H CRAFT M odel
272-101 full-feathering propellers with aluminum
blades which are driven through the n ose reduction
gears of the engine.
Designed primarily as a personnel transport,
the B-50 is readily adaptable for use as a light cargo,
ambulance, photographic or multi-engine training air-
plane.
1.2 GROUND HANDLING
Care must be used in ground handling of the air-
plane to avoid unnecessary damage. The following
pr ovisions and procedures are provided to reduce the
possibility of ground damage.
1.2.1 Hoisting Provisions -
1.2.1.1 Hoisting Airplane - The aircraft may be
hoisted for maintenance or parts replacement thr o ugh
the use of a three-cable sling attached to the h oisti ng
lugs
and eyebolt. A minimum overhead cleara nce of
12
feet 6 inches and a hoist of at least 3 tons capacity
is required for hoisting.
NOTE
If
it is necessary to hoist the aircraft with
one or both engines removed, it will be neces-
sary to use a sling under the tail. The tail
mooring hole can be used to hold the sling in
position.
1.2.1.2 Hoisting Engine - The engine may be hoist-
ed by removing the propeller and cowling and a ttach-
ing a hoist to the engine lifting eyes provi ded on top
of
the engine .
1.2.2 Jacking Pr ovisio n -
Provision is made for a three p oi nt jack-pad
system. The two aft pads are located on the ce nt er-
section rear spar inboard of each nace ll e. Th e for-
ward jack pad is located n ea r the af t ed ge of the n ose -
wheel well and to the left of the fuselage center line.
Jack pads are provided on eac h main gear a nd
nose gear so the wh eels may be raised individua ll y
by
use of an automo bile-type j ack for changing tires
or minor brake repair.
1.2.3 Leveling P rovisio ns -
Leveling the Twin-Bonanza while it is resting
on its wheels ls grea tly simplified by its tricycle gear;
it may be trimmed in both dire ctio ns merely by in-
flating or deflating the main gear or nose gear struts,
as required.
1
Lateral leveling is accomplished by using a
bubble lave! on the rear baggage compartment fl oor
board a nd deflating the lire or strut on the high side
of the airplane to center the bubble.
To level the Twin-Bonanza longitudinally,
attach a cor d and plumb bob to the Phillips head screw
just above the rear baggage compartment door. In-
flate or deflate the nose gear shock strut as required,
to pass the cord thr ough the center of a second
Phillips he ad screw directly below. Suspending the
plumb bob in a can of light engine oil will assist ln
stabilizing it.
1.2.4 Anchoring and Moo ring Pr ovisions -
Three m oori ng eyes are provided, one on
each wing and one in the tail bumper. Too moor the
airplane, chock the wheels fore and aft, install con-
tr ol l ock, and tie the airplane down at all three points.
Avoid ove rti g htenin g the rear rope and pulling the
n ose of the airpla ne up so far that wind will create
lift on the wings. If e xtr eme weather ls anticipated,
it is advisable to no se the air pl ane into the wind.
1.2.5 Parking Br ake -
The brakes ar e locked in the "ON" position
by pulling the parking-brake ha ndle o ut and p ump ing
the pilot's br a ke pedals until they hold a solid pres-
s ur e.
NOTE
Do n ot a ttempt to l oc k the pa rking br a ke by
a pplying force to the pa rking - br a ke handle. It
cont rols a valve only and cannot apply pressure
to the brake m ast er cylinder .
1.2.6 To wing -
To
wing lugs ar e provided on the nose strut
an d may be used for towing by hand or for towing
with a jug. Turn limits a re marked on the strut and
must not be exceeded . Using the hand tow bar one
man ca n tow the a irpl a ne on level co ncrete. When
moving the ai rpl a ne near other airplanes or buildings,
it is advisable to have o ne or two helpers to ai d in
directing movement of the a irplane to avoid damage
to the wings or tail .
1.3 SERVICING INSTRUCTIONS
1.3 .1 Servicing Fuel Tanks - r
The airplane fuel system should be serviced
with 80/87 oc tane fuel. The fuel system is suitabl e
for use with aromatic fuels . Fuel-system access
doo rs are of the flush type and are lo cated on the
upper surface of each outboard wing panel and each
side of the wing center section between the nacelle
and fuselage. Exp a nding-type filler caps with neo-
prene seals are used on each filler o pening.
The fuel ta nks are not interconnected and each
Revised 1 J une 1955

t an k mu s t be serv i ce d se pa rat el y. Th o Inboa rd or
ce nt er sectlo n ta nk s nro U1 0 m ai n tank s and sho uld
be fi ll ed firs t if a flig ht with re du ce d fu el lo ad ls lo
be made. The tanks arc read il y access ible for se r-
vicing over the l en din g ed ge of the win g.
NOTE
Sin
ce fu el wi ll r emove the pl as ti ci z er fr om the
rubber cells, on ce th e a irpl ane Is pla ce d in se r-
vice, th e fuel ce ll s s ho uld be re filled i mmediat e-
ly after eac h fli ght. If extended p er iods of
storage ar e re quired, the fuel ce ll s should be
drai ned, and the i nt e ri ors co at ed wi th a thin
coa t of engine oi l.
T he fuel tank s may be dr ained by opening the
d
rain coc k l oca ted in the s ump of each tank.
1.3. 2 S ervici ng O il Sy stem -
Th e en gi ne is provi ded with a wet s ump, pre s-
sure-type oil syste m wit h an o il coo le r to ai d in
co n trolling oil operati ng te m pera tur es. The s ump
capacity is 12 qu arts max im um . Use Grad e 1100
(
SA E 50) and Gr ade 1065 (SAE 30) av ia ti on o il in
summer and winter res p ectively. The o il s ump dlp
stick is calibrated for u se in an airpl a ne with ei the r
tricycle or conventiona l lan din g gea r. Always che ck
the oil level on the side of th e dip s t ic k ma rked
"Tricycle".
To service the engi ne wi th oil, open th e quick
re l ease oil access d oor on to p of the co wl ing and re-
move the cap on top of th e engine.
Oil may be drai ned by o pening the cowling
and removing the oil drai n p lu g on th e bo tt om of the
engine oil reservoi r an d oil coo ler . It is re co mmend-
ed that the engine be war med up to o peratin g te m-
peratures to insure co mpl ete dr a inin g of the o ld o il.
1.3.3 Servicing Bra k es -
The hydraulic bra ke syste m co ns is ts of two
Goodyear single-disc bra k es, wh ic h m ay be ope rated
by either the pilot's or copilo t 's to e br akes on the
rudder pedals. The brake fl uid reservo ir is loca ted
in the nose baggage compar tm e nt and sho uld be fill ed
to within one inch of the top wi th Sp ec ifica ti on MIL-0-
5606 hydraulic fluid.
1.3.4 Servicing Tires -
The main wheel tires are 8:50 x 10 , 6- ply,
The nose wheel tire is a 6:50 x 10. Inflate a ll tir es
to 35 psi. Maintaining proper tir e infla ti on will av oid
considerable damage from la n ding s h oc k and fr om
running over s harp stones and rut s. When infla ting
tires, inspect them visually for cr ac k s, b rea k s, or
evidence of internal damage .
1.3.5 Servicing Landi ng Gea r Sh oc k Ab so rber -
The landing gear s hock ab so rber s a re of the
air-oil type. They shou ld be ser vi ce d wi th hydr a ulic
fluid Specification MIL -O-5 606.
To ch ec k the fluid level, de flate the strut by
releasi ng air t hr ough va lv e; a fter the air pres s ure
is re l eased, re m ove th e filler valve adapter.
2
NOMENCLATURE KEY
Ma
in Landing Ge ar a nd Door
1. Ma in Landing Gear D oo r Link age -100 hou rs.
2. Main Land ing G ea r Lift Le g - 50 ho ur s.
3. Main Whe el Bea rin gs -100 ho ur s.
Ailer on Co ntr ol Quadr a nt
1. Ailer on Co ntr ol Quadr a nt -200 ho ur s .
Co
ntr ol Co lumn
1. Co ntr ol Co lumn -200 ho ur s.
E mp e nn age Co ntr ol Surface s
1. Rudder Tab Actuator - 200 ho ur s.
2. Rudder Tab Li nka ge Uni ve rs al Joi nt s and Tab
Hinge
Wir e - 100 ho ur s.
3. Elevat or Tab Linkag e Uni ve r s al Jo int s and
Tab Hinge Wire - 100 ho ur s .
4.
Elev a tor Tab Actuator -200 ho ur s .
Aileron Tab Actuator
1. Aileron Tab Actuat or - 200 hour s .
2.
Aileron Tab Cable Link ag e - 100 ho ur s .
Ailer on Bell Crank
1. Aileron Bell Crank - 100 hours.
Carburetor A tr Valve
1. Carburetor Air Valve - 100 hour s. (Bulletin B50,
No. 19
replaced these parts with sealed
bearings which r e quire no lubr i cation ).
Tachometer Generator
1. Tachometer Generator -50 Hours.
J - Propeller
1. Propeller and Transmission Gears -100 hour s .
Landing
Gear Retract Mechanism
1. Landing Gear Limit SWitch Screw - 100 hours.
2. Landing Gear Clutch Finger - 100 hours.
3. Nose Gear Retract Chain - 100 hours.
4. Landing Gear Clutch Disengaging Bushing -
200
hours.
5. Landing Gear Clutch Fingers - 100 hours.
6. Landing Gear Emergency Extension Drive -
200
hours.
7. Landing Gear Emergency Handle Pin - 200 hours.
8. Landing Gear Gearbox -500 to 1000 hours
depending on operation .
9. Landing
Gear Actuators -500 to 1000 hours
depending on operation.
L - No s e Wheel Steering Mechanism
1. Nose Wheel Steering Mechanism -50 hours.
M- Nose Landing Gear and Door
1. Nose Gear Door Linkage and Hinges - 100 hours.
2. Nose Gear Steering Linkage Idler - 100 hours.
3. Nose Gear Lift Leg -50 hours.
4. No se Gear Torque Knees -50 hours.
5. Nose Wheel Bearings - 100 hours.
N - Rudder Pedals
1. Rudder Pedal s - 200 hours.
0 - Fl ap Ge arbox (Hours depend on type of operation)
1. Flap Gearbox -500 to 1000 hours
2. Flap Actuator Drives - 500 to 1000 hours
3. Flap Actuator s - 500 to 1000 hours
4. Flex Drive Shafts -500 to 1000 hours

Figure 1-2 . I.Albrlcatlon Chart
3
- 3 rt
OGP
.................... 'I .-
... ~4®;-------.
I GU • .
.. .
....
1 PUCl
DETAIL I
IDENTIFYING
SYMBOL
SP
GB Gr ease
FG Gr aphite
OGPou
OE A OU
GLT Grease
GH Grease
OGR O IL
0
HOURS
r--
GREASE
GUN
LEGEND
TYPE OF
LUBRICANT
BASIC
SPECIFICATION
SPECIAL
MIL -L-77ll
Ml L--C -67 ll
MIL-L-7870
MIL--0-6 082
MIL-G- 3278
MIL- L-3545
MIL- O-6086
FREQUENCY 0
S PECIAL
METHOD
I
~
f
HAND
OIL
BRUSH
OR CAN
PACK
SPECIAL SERVI CE NCYI'ES
FITTINGS - C lea n fittings before l ubricating .
Lubrtcate through fittingsuntil new
greau appeara
at the part being lubricated.
PIANO TYPE !UNG ES - Care IJh ould be taken to
remove all excess lubricant after lubricating as
lt will accumulate dirt and sand and cause unduft
wear .
CONI'R)L SYSI'D,f BEAR!NlS -The ball bearings
In thla aircraft are sealed and do not require re-
lubrtcatlon. Keep all control bearings wiped ofi
and clean .
USE
OF GRAPlilTE - Mix powdered graphite
with quick evaporating- liquid (naptha) and apply
wllh brush.
PROPELLER EXTERNAL GEARS • Use moly
kote mixture; see PROPELLER MAINTENANCE,
SECTION IV.

(e) Install the mounting screws that secure the
false panel to the aircraft structure.
(f) Install the plastic placard strip over switches
Jlnd engine controls. Secure the fasteners by pushing
into locktng
position.
5.6 INSTRUMENT VACUUM SYSTEM -
The vacuum system consists of two engine-
driven vacuum pumps ( one on each engine), an oll se-
parator in each engine accessory section, a suction
relief valve In each wh eel well, a filter behind instru-
ment panel, a suction gage on instrument panel, and
necessary interconnecting tubing and hose . It powers
the gyro-controlled flight instruments.
5.6.1 Adjustment of Suction Relief Valve -
(a)
Loosen locknut and turn adjusting screw
counterclockwlse to increase suction, or clockwise to
decrease suction.
(b) Adjust suction relief valve to draw 4. 25 inch es
of mercury at cruising speed.
5.6.2 Removal of Vacuum Pump -
(a)
Disconnect suction and discharge lines.
(b) Remove nuts from the four mounting s tuds .
(c)
Pull pump out and off engine mounting pa d.
NOTE
Before installation of pump, make sure lu b ri-
cati on hol"'.s in pump flange are not covered
by the flange gasket.
5.6.3 Installation of Vacuum Pump -
(a)
Place gasket in position on mounting st uds.
(b) Place pump on engine mounting p ad .
(c) Install and tighten nuts .
5.6.4
(a)
(b )
Removal of Oil Sep arator -
Disconnect inlet, outl et, an d oil r e turn lines.
Remove two bol ts from mounti ng brackets.
Revised 1 June 1955 4
(c) Lift unit from mounting.
NOTE
Clean oil separato'i- in unlea ded gasoline or
other suitable solvent and dry thor oughly
with compressed air each 100 ho ur inspection.
5.6.5 Installation of Oil Separator -
(a)
Place unit in mounting bracket.
(b) Install bolts in mounting bracket and tighten.
(c) Connect inlet, outlet, and oil return lines.
5.6 .6 Removal of Suction Relief Valve -
Disconnect lines at inlet and outlet el bows .
Unit
will fall free.
5.6.7 Installation of Suction Relief V alve -
Connect
lines at in let and outlet elbows.
5 .6 .8
(a)
(b )
R emoval of Filte r -
Di
sconnect i nstrument lines at manifo ld.
R
em ove nuts fro m the two moun ting bolts .
(c) Remove
fllt er bowl to cl ean or re pl ace filter
elem en t.
NOTE
The fllt er should be cleaned every fifty ho ur s .
To
cle an ele me nt bl ow air th ro ugh elem e nt in
the di re cti on oppo sit e no rm al flow. Ca r e should
be taken not to bl ow a ir i nt o element at ri ght
angl
es , as this w lll tend to clog dus t in element.
Tilt a ir ho se at appr o ximately fo rty-fi ve de-
grees. After dust has been blown from ele-
ment, wash in alcohol, then dry with compress-
ed ai r,
5.6.9
(a)
(b)
(c)
Installation of Filter -
Place unit on mounting bracket.
Install nuts on the two mounting bolts.
Connect instrument lines at manifold.

PART II
AIRFRAME
2.1 GENERAL
This section is devoted to the maintenance of
the various components of the airframe group, in -
cluding the fuselage, tail group, control surfaces and
systems, wing sections and landing gear.
2.2 FUSELAGE
The fuselage is all - metal semimonocoque con-
struction and is divided into the following sections:
nose baggage compartment, pilot and passenger
compartment, rear baggage compartment and fuse -
lage tail section. Carry-through structure vf the
center -wing section passes through the lower section
of the fuselage and is attached to the fuse l age by
shear connections that can be removed to detach the
center section (see Figure 2-1).
2.2.1 Pilot and Passenger Compartment -
The cabin compartment is arranged to
accommodate six persons, three in each seat. Th e
front seat is arranged to accommodate the pilot on
the left, an assist pilot in the center and one passen-
ger on the right. The left two-thirds of the front seat
is adjustable to fit the requirements of the pilot.
The right third of front seat is hinged so that it will
pivot forward on a skewed axis to permit access to
the rear passenger seat. The control console is
mounted in the instrument panel slightly to the le ft
of
center and contains the control column, engine
control levers and aileron and rudder tab cont r ols
and position indicators.
2.2.2
Cabin Entrance Door -
Entrance to the cabin is made through a
large door on the right-hand side of the fuselage.
A wing walkway and an automatic, el ectrically-
retracted step complete the entrance to the cabin.
The door is of all-metal construction, the door sk in
spotwelded to the channel-type frame. The lever -
type door handle and the hinges are flush-mounte d
so the door is completely flush with the fuselage
skin when closed.
2.2.2.1 Removal -
(
a) With the door in a nearly-closed pos i tio n,
press down on the portion of the st op rod that ex-
tends into the door until the stop rod ca n be r emoved
from its track.
(b) Remove upholstery for wa r d of doo r jam b
to gain access to the door hinges.
(c) With one man supporti ng the d oor on the
outside, remove the door hinge pins.
2.2.2.2 Minor Repairs and Pa rt s Replac em e nt s -
(a)
Replace wor n or damage d d oor weat her
seal. The weather seal mu st fit smoo t hly aro und
the entire door to pr event air lea ks.
(b) Replace wor n or da ma ge d hinges or d oor
latch.
(c) Rep air s to the d oo r skin m ay be made by
approved me th ods fo r sk in re pair s.
1
2.2.2.3
(a)
pins.
(b)
In s tallation -
Position door and align holes for the hinge
Install the hinge pins and safety.
(c) With the door in the nearly closed posi-
tion, press the door stop rod down far enough to
allow the end of the rod to enter the door stop track.
2.2.2.4 Adjustments -
Several adjustments are available to
assure proper closing and sealing of the door.
(a) If the door does not close tightly or per -
mits air leaks when completely closed (with door
seals in good condition), it is probably due to insuffi-
cient tension on the aft door latch and may be
cor r ected by loosening the four retaining screws and
movi ng the la tch tongue guide outboard to create
a dd itional tension on the la tch tongue.
(b) Air le ak s ar ou nd the upper portion of the
doo r may be c au se d by in ad eq ua te tension on the
upp er door la tch. This ma y be corrected by remov-
ing the sm a ll uph ol st er y p an el above the door window
an d sho r teni ng the up pe r l at ch cont r ol wire suffi-
cie n tly to pr ope r ly seal the d oo r.
(c) Sagg i ng or im pr oper f itting of the door may
be co rr ecte d by add ing th in shi ms unde r the lower
hi n ge to r ai se the aft por tio n of the doo r .
2,2.3 C
abin W in d ow s and Windsh ie ld -
Th e w ind ows and wi ndshield ar e formed of
cle ar a crylic p la s ti c and mad e up in se ve n r emovable
sectio ns . Th e r e ar wind o ws are hin g ed at th e top so
th ey ma y be opened on th e g round for add itional
coo lin g. Th e l owe r st op is readil y rem ov a ble so the
r e ar wi nd ow ma y be opened full y fo r em er gency
ex it. A loc k is pr ovi ded on the lower st op to pr event
th e windo w be in g ope ned inadvertentl y in fl ight.
2.2 .3.1 Re mo v al -
(a) Remove
sheet metal scr e ws attac hing the
inner t rim s trip and rem o ve the tr im str i p.
(b) Wi th one man workin g inside an d one ou t-
si de r emove the flush ty pe machine scr ew s r e ta in-
ing the frame.
(c) Re mov e wind ow and frame. Care mus t
be
used wh en br e akin g window seals not to break
or dama ge the plastic of the wi ndow.
2.2.3.2 Installation -
(a) C
lean wind ow frame and skin ar oun d win -
dow or windshield o penin g to a ssure sa ti sfac to r y
se alin g of new window .
NOTE
New wind ows or windshield will require fit t ing
wh ic h mu st be ac c omplished before apply ing
ce men t.
(b) Apply thin coat of sealin g cement ,
Minn eso ta Mining and Manufacturin g Co ., EC-870 ,

around the window opening.
(c) Install the window or windshield section
and with one man inside the airplane, install the re-
taining screws and nuts. Tighten all the screws
evenly to prevent excessive strain on the plastic.
(d) Clean excess sealer from the window and
window frame with wooden scraper.
(e) Install the window or windshield trim
strips.
2.2.3.3 Cleaning -
Cleaning of the acrylic plastic should
never be attempted on dry windows. The window
should first be flushed with water or a mild soap
solution, then rubbed lightly with a grit-free soft
cloth, chamois or sponge. Stubborn grease or oil
depo s its are readily removed with naphtha or hexane.
Rinse with clear water.
2.2.4 Cabin Seats (Front) -
The front cabin seats are cushioned with
foam rubber and internal springs. They are attached
directly to the front spar of the center section.
Built in two sections, the left two-thirds is adj u st-
able fore and aft through approximately 3 -1 / 2 inches
of travel. The track is inclined so the seat moves
upward as it is adjusted forward. The right-hand
third of the seat swivels forward and to the left on a
skewed axis to allow passenger access to the rear
seat.
2.2.4 .1 Removal -
(a) Remove the two hold-down bolts that attach
the right-hand seat to the sidewall of the fuselage
and center -section spar.
(b) Remove right-hand seat.
(c) Adjust the left-hand portion of the seat to
the full forward position.
( d) Release the spring-loaded pin fasteners on
each side of the seat adjustment casting.
(e) Release the quick-lock fasteners on the
slide by turning the rings counterclockwise.
( f) Pull out on the rings and lift the forwar d
portion of the seat up.
(g) Pull forward to remove the seat.
2. 2.4.2 Installation -
(a) Place left-hand portion of seat in position
and insert the aft end of the slide in the holes pro-
vided in the front spar. Align the holes in the front
of the slide and lock the quick-lock fasteners.
(b) Pull out the spring lock on the seat
adjustment attachment point, align with the adjust-
ment casting and release to lock in position.
(c) Check adjustment for freedom of movement.
( d) Place right-hand seat in position and
install attaching bolts at the fuselage sidewall and
spar attaching bracket.
2.2.5 Cabin Seats (Rear) -
2.2.5 .1 The rear cabin seats are constructed in
two sections, cushioned with foam rubber and inter-
nal springs in the same manner as the front seats.
2
The lower portion is attached to the rear center -
section spar. The seat back may be tilted aft at the
top.
2.2.5.2 Removal -
(a) Working from the baggage compartment,
remove the bolt on each side which attaches the
seat back adjustment to the fuselage .
(b) Working inside the cabin, release the
trunk-latch type fasteners which attach the seat
bottom to the front of the seat mounting structures.
(c) Pull the seat bottom forward to disengage
the rear mounting pins.
(d) The seat then may be turned and the seat
back folded down. Remove through the rear baggage
compartment door .
2.2.5.3 Installation -
(a) Insert the rear attaching pins in holes in
the seat mounting pads on the rear spar.
(b) Fasten the trunk latch fasteners which
secure the front of the seat to the seat mounting
structure.
(c) Install the bolts which attach the seat back
adjustment to the fuselage structure .
2.2.5.4 Adjustment -
Pull the seat forward to release the
latches and move back to the rearward position. To
return the seat to the forwa rd position , pull forward
to the latches.
2.2.6 Nose Baggage Compartment -
The nose baggage compartment occupies
the space immediately for wa rd of the cabin. It
provides 14 cubic feet of cargo space.
Access is through a door in the right side
of the fuselage ahead of the wing. A dome light in
the center of the compartment overhead is controlled
by a micro switch in the door casing operated by the
door latch. The starter contr ol circuit also is routed
through this switc h. Opening the baggage door turns
on the co mpartment light and breaks the starter
relay control circuit, so that the engines cannot
be started until the door is closed and latched.
2.2 .7 Rear Baggage Compartment -
The rear baggage compartment, immediately
aft of the cabin, contains 41 cubic feet of cargo space.
The do or is located in the right side of the fuselage,
just aft of the wing. The compartment is lighted by
a dome light controlled by a switch in the door
casing.
2.2.8 Rear Fuselage Section -
The rear fuselage section is accessible by
removing the rear bulkhead in the baggage compart-
ment. It contains the tail surface control cables,
turnbuckles and bellcranks . Access to the aft end
may be gained by removing the tail cone and five
inspection doors; two on each side below the
horizontal stabilizer and one on the left side above
the horizontal stabilizer.

CABIN COMPT.
TAil SECTION
Figure 2-1. Compartment Diagram

. . ·.
.. ·.
• ....· ... •, ·.- ... ·.
....
..
··.·
. ·.
. .·· ...
: .. .:. -:: ..
••.:i /i ... ······ ..
. . .
. .
·· ... ·.• .. .. ·
Center Sec ti on Wing
Figure 2-2.

Figure 2- 3. Outboard Wing Panel and Tip
Figure 2-4. Wing Htnge Ptn Installation
5

2.3
CENTER WING PANEL
The primary structure of the center wing
section consists of the front and rear spar and a
stressed skin covering . This structure forms a
two-spar torsion box with the nacelle structure
mounted on the front spar. The NACA 23000 series
airfoil used on the outer wing panel is continued
thr o ugh the center panel. Bladder -type fuel tanks
are located between the spars outboard of the fuse -
lage .
2.4 ENGINE NACELLE
An integral part of the center wing panel, the
engine nacelle, houses the engine, its mounting
structure, and the landing gear . The portion of the
nacelle from the firewall aft is attached by rivets
and is not readily removable. Doors oper ated by the
landing gear retract syste m and hinged to the lower
side of the nacelle enclose the landing gear when it
is retracted.
2.5 OUTER WING PANEL
The outer wing panels are NACA 23000 air-
foils and are constructed with a single , load-carry-
ing front spar and aluminum - alloy sheet skin cover -
ing . The rear spar or shear web transfers the shear
load between the upper and lower skins. Attachment
to the wing center section is made by four tension
bolts located at the upper and lower caps of the front
and rear spar. Outer wing bending loads are trans-
mitted to the center section through tension on the
bolts , or bearing of the faces of the outer wing and
center section fittings on each other . The wing
shear loads are carried by the serrated faces of the
wing attachment points on a soft aluminum wa sher.
A bladder-type fuel cell is installed in the
leading edge of each outer wing panel just outbo ard
of
the wing attachment fitting .
2.5 .1 Removal of Wing -
(a)
Drain fuel cell.
(b) Disconnect aileron and aileron tab cables
(l eft wing only) at turnbuckles inside the wheel well.
(c) Remove augmenter tube cover plate and
augmenter tube clamps. The augmenter tube is re-
moved for access to fuel and fuel vent lines .
(d)
Disconnect fuel lines , fuel vent lines and,
on the left side only. the airspeed pilot line .
(e)
Disconnect the navigation light , landing light
and pitot heater wires at the electrical junction
block inside the access hole on the lower side of the
engine nacelle.
(f) Remove access hole cover on lower wi ng
skin just forward of the rear s pa r at the wi ng
attachment fitting. Disconnect the flexi ble fla p dri v e.
(g) Remove the wing att aching bolt cove r pla t es
and attaching bolts .
N
OTE
Special wrenc h es are requ i red for the NAS
high stre n gt h bo lt s u sed on the wing attach-
ment fittings.
6
CAUTION
Be sure the wing is properly supported at
the butt and tip before the wing bolts are
removed . Move wing straight away from
the airplane until all fuel lines are clear
of the center section.
2.5 .2 Disassembly -
(a) Support the wing on a suitable cradle.
(b} Remove wing tip .
(c)
Remove screws attaching aileron to bracket,
disconnect aileron tab cables (left aileron only}.
Remove aileron .
(
d} Remove the bolt attaching the flap jack-
screw to the flap . Remove the patch plates on top of
the flap and remove the bolts attaching the flap to
flap track.
(e) Remove access cover and scupper plate
over fuel cell . Remove filler neck and fuel level
transmitter . Unsnap the fuel cell from the upper
skin. Disconnect the fuel outlet and vent lines. Re -
move the fuel cell through the access hole.
(f) Remove the screws around the sp ar cap and
rib at the wing attac h ing point and the screws at the
tip rib.
(g) The steel retaining wire may be removed
by grasping with plie r s an d pulling. (Vise grip
pliers are recommended.) Remove the wires re-
taining the le a ding edge fi r st , then r emove the wires
holding the sp ar to the re ar wing sectio n. Do not
attempt to spi n the wir es out wi th a dr ill mo tor; the
heating and expansion of the wi r e will c ause it to
seize in the hi n ge and b reak .
2.5 .3 Re as se mb ly -
(a) Be
fo r e as semblin g the spar to the wing
se ctio n s, it is advisabl e to drive a retain i ng wire
thr ou gh the hinge s ection s to remove an y burrs or
foreign ma tte r .
(b) Use a new re t ain i ng wire and coat liberally
wit h p ar af fin or powdered g raph i te .
(c)
Ass em bl e the spar to the rear wing sec ti on
an d alig n the h ing e se c tions .
(d)
Us in g an E- 2 r ive t gun ( or gun of equi v alent
si ze) drive th e w ire i n. The wire mus t be suppor t ed
during the d rivi ng operati on and t he use of the
fo ll ow ing si ze s of telesc o pin g tubes are recommended :
3/ 16 x .049 st
ee l tubin g - 60 , 32, 17, 9, 5, 2- 1/ 2 in. ;
1/ 4 x .049 st
ee l tubin g - 60, 32, 17, 9, 5, 2-1 /2 in .
Th e ret a in in g wire is inser t ed in the assembled steel
t ub ing gu i des and as the wire is driven in, sections of
the tub ing are remo v ed .
CAUTION
Do
not use a drill motor to spin the wire in
as the heat and expansion may cause the wire
to seize and break.
(e) Install the leading edge in the same manner
as the rear wing section.
(f) Replace machine screws around the spar
fittings and tip and butt rib.

2,5,4 Repair -
The wing ts e ntir ely stressed skin constr uc-
tion. Any
repair to the skin or internal struct ure
should be made by a BEECHCRA FT CertUled S ervice
Statton, or by a facility properly equipped to accomplish
structural repair.
2,5.5 Installation -
(a)
Place wing in position for installation and in-
stall the wing attaching bolts.
WARNING
New aluminum washers mu st be installed be-
tween the upper center section and outer wing
panel fitting each time the wing bolts are
loosened enough to allow the serrated faces
of the upper wing attaching fittings to change
position in relation to each other .
(b) Tighten the wing attaching bolts to the
following torque:
1 Lower forward spar bolt, 5,000 to 5,500
inch-pounds.
2 Upper forward, upper and lower r ear spar
bolt, 2,000 to 2,300 inch-pounds.
(c) Connect electrical wiring at jwtctlon block
in lower side of engine nacelle.
(d) Connect fuel outlet and fuel vent line, and
pitot line (left wing only).
(e)
Connect aileron and (left wing only) aileron
tab cable turnbuckles in landing gear wheel well.
Rig to proper tension.
(f) Connect the flap flexible drive.
(g) Check flap travel and stops. Check opera-
tion of navigation lights, landing lights, and pitot h ea t.
Fill the fuel tank and check for l eaks. Check the
airspee d system for proper operation, preferably
against a master instrument. When using a master
instrument for checking the airspeed the tempera-
ture must remain constant and differential must not
exceed five mph in 15 minutes .
(h) Install augmenter tubes and all access hole
covers.
NOTE
Retorque the wing bolts as indicated in
Paragraph 2.5.5 after first 100 hours of
flight time after wings are installed,
2,5,6 Adjustments -
Rigging adjustment of the wing is not o rdinar-
ily necessary; however, when flight tests indicate a
wing-heavy condition, the wing may be washed in or
out for correction. Proceed as follows:
(a) Mark the present position of the wing on the
wing attachment fittings.
(b) Loosen the wing attaching bolts.
(c) Remove the bolts one by one and replace the
soft aluminum washers between the wing attachment
fittings.
7
(d) Determine the new positlon of the wiJg and
tighten the wing bolts.
(e)
NOTE
If wing is heavy, the leading edge must be
raised above its original position, as indi-
cated by the marks made before loosening the
bolts. If wing is light the leading edge should
be lowered,
Test fly aircraft. Readjust if necessary.
NOTE
New
soft aluminum washers must be in-
stalled when the wings are rotated and a log
book entry made so the wings may be re-
torqued after the first 100 hours of flight
time after the washers are installed. The
stall warning indicator also must be checked
and the detector vane reset if necessary.
2,6 WING TIP
The wing tip is formed of soft aluminum and is
readily removable for repair.
2.6.1 Removal -
(a)
Remove the machine screws attaching the
wing tip to the wing.
(b) Unscrew the electrical lead to the naviga-
tion light from the navigation light base.
2.6.2 Installation -
(a) Attach
the electrical lead to the navigation
light base and tighten.
(b) Install machine screws which attach the
wing tip to the wing.
2,7 CONTROL
SURFACES
NOTE
All control surfaces, both fixed and movable,
are of stressed-skin construction. There-
fore, all repairs must be made by a
BEECHCRAFT
Certified Service Station or
other facility properly staffed and equipped
for structural repairs.
2. 7.1 Horizontal Stabilizer -
The horizontal stabilizer is of all-metal
construction with two channel section main spars.
The metal skin utilizes internal bead stiffeners. The
stabilizer is attached to the fuselage by bolted shear
connections at the front and rear spar.
2.7.1.1
(a)
the tab.
(b)
Removal -
Remove the elevator tab actuating arm at
Remove the plastic tau cone.

17
l
2
-
~
;---,
"'-..--- 3
~-'---+ - 4
5
6
:> ~ ~ < ··.·
~
_)---- 11
·7
15 14 13 12
1. Dorsal Fin
2. Vertical Stabilizer
3. Rudder
4. Rudder Hinge
5. Rudder Trim Tab Actuator
6. Rudder Trim Tab
7. Elevator Hinges
8. Elevator
9. Elevator Trim Tab
10. Elevator Torque Arm
11. Tail Light
12. Tail Cone
13. Elevator Actuator
14. Horizontal Stabilizer Fitting
15. Rear Fuselage Assembly
16. Elevator Trim Tab Actuator
17. Horiz o ntal Stabilizer
18. Rudder Bell Crank
19. Rudder Bell Crank Bracket
Figure 2-5. Empennage Section
8

(c) Remove the elevator (see Paragraph
2.7.4. 1) .
(d)
Remove the rear fuselage access cover
and disconnect the elevator tab cables al the turn-
buckles. Remove the tab cable pulleys on aft fuse -
lage bulkhead .
(e)
Remove tail sectio n hand hole covers
above and below stabili zer to gain access to the
stabilizer attaching bolts .
(f)
Remove the shear bolt s attaching the front
and rear stabilizer spars.
(g) Pull stabilizer directly away from the air -
plane
until comp letely clear .
2.7.1.2
Installation -
(a)
Position stabilizer for installation and
align
bolt holes .
(b) Install mounting bolts and tighten .
(c)
Route tab cables back through the fuselage.
Connect turnbuckles and install pulleys .
(d) Install the e le vator (see Paragraph
2 7.4.2).
(e)
Check the rig and operation of the trim
tabs (see Paragraph 2.8.4.4).
2.7.2 Vertical Stabilizer -
The vertical stabilizer is of all-metal con-
struction with two channel section main spars. The
metal skin utilizes internal bead stiffeners. The
stabilizer is attached to the fuselage by bolted shear
connections at the front and rear spar .
2.7.2.1
Removal -
(a)
Remove the rudder as outlined in
Paragraph 2. 7.5 .1.
(b) Remove the access plates on the left side
of the fuselage above the horizontal stabilizer.
(c) Disconnect tab cables .
(d) Remove the bolts attaching the vertical
fin to the rear fuselage bulkhead .
(e)
Remove the attaching bolts at the forward
fin attachment point.
2.7.2.2
(a)
points .
(b)
Installation -
Install bolts at front and rear attachment
Connect tab ca0les.
(c) Install the rudder as outlined in
Paragraph 2.7.5.2.
(d) Install the tail cone and access plates.
2.7.3 Aileron -
The aileron is constructed primarily of
FS-la magnesium alloy sheet. Other materials are
used locally for reinforcement of hinge brackets,
balance weight supports and other stressed structural
parts . Each aileron has a single channel-section
spar of FS-la magnesium alloy . The skin is formed
in one piece and beaded chordwise for reinforcement.
2.7.3.1
(a)
only).
(b)
Removal -
Disconnect the trim tab cables (left aileron
With one man supporting the aileron, re-
9
move the attaching screws at each aileron hinge
bracket.
(c) Move the aileron straight away from the
bracket until completely clear. Care must be used to
avoid damage to the skin by causing binding or strain
in attaching area .
2.7.3.2
Installation -
(a)
Place aileron in position on the hinge
brackets. Be sure that the hinge bracket is in its
proper place between the aileron skin and the inner
reinforcing structure.
(b) Install two upper and two lower attaching
screws at each aileron hinge bracket.
(c) Connect aileron tab cables (left aileron
only). Check ~peration of the aileron tab to be sure
it is operating in the direction indicated by the control
and the cables are not crossed.
2.7.4 Elevator -
The elevator is built principally of FS-la
magnesium alloy, with a few stressed parts of
24ST aluminum and mild steel. The skin , spar,
small ribs and most detail parts are magnesium
alloy . The three main ribs and balance horn are
24ST aluminum . The hinge brackets are mild steel.
The skin aft of the spar is beaded for reinforcement.
2.7.4.1 Removal -
(a)
Remove tail cone attaching screws, dis-
connect tail navigation light wire and remove tail
cone.
(b) Disconnect the tab actuator rod.
(c) Remove the four bolts attaching the eleva-
tor extension tube adapter to the elevator horn.
(d) Remove the hinge bolts, disconnect the
bonding cable and pull the elevator away from the
stabilizer.
2. 7 .4.2 Installation -
(a) Align
holes in elevator and stabilizer
hinge, install attaching bolts and connect the bonding
cable.
(b) Install bolts which attach the extension
tube adapter to the elevator horn.
(c) Attach elevator tab actuator.
2.7.5 Rudder -
The rudder is bunt principally of FS-la
magnesium alloy , with a few stressed parts of 24ST
aluminum or mild steel. The skin, spar, small ribs
and most detail parts are magnesium alloy. The
three main ribs and balance horn are 24ST aluminum.
The hinge brackets are mild steel. The skin aft of
the spar is beaded for reinforcement.
2.7.5.1 Removal -
(a) Remove tail cone attaching screws and
disconnect rear navigation light wire. Remove the
tail cone .
(b) Disconnect rudder tab actuating rod aft of
the actuator.
(c) Remove the attaching bolts at rudder horn.
(d) Remove rudder attaching bolts from the
rudder hinge and remove rudder.